High altitude parachute navigation flight computer

ABSTRACT

A navigational computer design for high altitude and other similar navigational needs includes a processor, which receives as input signals from navigational and navigational related sensors such as a GPS, compass, inertial measurement unit and sensors. Processor utilizes the navigational information to provide a display to the user indicating present navigational positional information as well is providing a flight path to follow to the target. The navigational computer includes a device that enables it to operate in a peer-to-peer network with other similar navigational computers such that during use, users may track one another. Once on the ground, the navigational computer may be used to continue navigation.

RELATED APPLICATION AND PRIORITY CLAIM

This application is a divisional of U.S. Pat. No. 10/914,643 filed onAug. 9, 2004 which claims priority from U.S. provisional patentapplication No. 60/493,366 filed Aug. 8, 2003 both incorporated fullyherein by reference.

FIELD OF THE INVENTION

The present invention relates to navigation computers and moreparticularly, to a navigation computer for a parachute jump at highaltitude.

DISCUSSION OF RELATED ART

Navigation computers have long been used for parachute jumps. Thecomputer may provide the parachutist with information regarding thestatus of the jump, such as altitude and distance to target, as well asinformation required for the parachutist to reach the target. Formilitary purposes, high altitude/high opening (HA/HO) jumps are used forinsertion of elite troops into enemy or friendly territory. In such ajump, troops leap from aircraft at extremely high altitudes, above30,000 ft, to reduce the chance of aircraft detection or attack. Theteam requires oxygen and special equipment for such a jump. Theparachutes are opened shortly after jumping, and the team performs aseries of navigational turns to remain on a proper course to arrive ontarget. Given the significant flight times from the high altitude, anumber of navigational changes must be made to arrive as close aspossible to the target. Currently, teams have little ability to navigateto a target unless it can be seen upon exit from the aircraft or duringdescent.

Furthermore, the navigational changes, including changes in altitude,must be coordinated between members of the team. During such jumps, theteam must stay together as much as possible. It is desirable for theteam to fly together in a close formation. During their dissent,however, the team must stay far enough apart so as to avoid a collision.The team must make complicated maneuvers to control speed, direction,and member spacing, and to arrive at the desired target site.

While a navigational computer could aid jumpers in HA/HO jumps, knownnavigation computers are inappropriate for such conditions. Given theequipment carried by the troops, and the need to control the parachute,operation of one or more buttons or controls of a navigation computer isdifficult since the prior art devices were generally worn on the stomachof the jumper. At high altitude, think gloves necessary are necessarybecause temperatures can reach −58 F. Unfortunately, these thick glovesmake operating buttons problematic and viewing a belly-mounted device isproblematic due to required oxygen masks. Additionally, jumpers oftencarry cargo that is attached off a tether to their chest harness. Theteathers can interfere with a belly mounted unit. Furthermore, knownnavigational computers cannot operate at the extreme temperatures oraltitudes of HA/HO jumps. Also, known navigational computers do notallow for coordinated operations between members of a jump team.Finally, the navigational computer only operates while the jumper isdescending. It becomes useless, and is simply excess weight, once thejumper is on the ground.

Accordingly, what is needed is a system and makes it possible tonavigate in close formation and at high altitude precisely during zeroor near-zero visibility situations (e.g., adverse weather conditionssuch as cloud cover, rain, snow, fog, and darkness), thereby greatlyreducing the possibility of detection. What is also needed is a systemand method that adds peer-to-peer networking capability between suchindividual units in systems, thereby creating a system wherebyindividual team members may see each others location throughout flightand after landing.

SUMMARY OF THE INVENTION

It is important to note that the present invention is not intended to belimited to a device or method which must satisfy one or more of anystated or implied objects or features of the invention. It is alsoimportant to note that the present invention is not limited to thepreferred, exemplary, or primary embodiment(s) described herein.Modifications and substitutions by one of ordinary skill in the art areconsidered to be within the scope of the present invention, which is notto be limited except by the following claims.

BRIEF DESCRIPTION OF THE DRAWINGS

These and other features and advantages of the present invention will bebetter understood by reading the following detailed description, takentogether with the drawings wherein:

FIG. 1 is an oblique view of a navigational computer according to anembodiment of the present invention attached to a jumping harness;

FIG. 2 is an oblique view of a navigational computer according to anembodiment of the present invention without the cover;

FIG. 3 is a front view of a display of a navigational computer accordingto an embodiment of the present invention;

FIG. 4A is a front view of a display of a navigational computer having asatellite image according to one embodiment of the present invention;and

FIG. 4B is a front view of a display of a navigational computer having acompassed based image according to another embodiment of the presentinvention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

The present invention features a navigation computer system that isparticularly useful for HA/HO jumps, although this is not a limitationof use of the present invention. As illustrated in FIG. 1, thenavigational computer 10 is preferably small enough such that it may beattached to the helmet 331 of the parachutist 30. This embodiment ispreferably since it minimizes the amount of wires/cables. Alternatively,the navigational computer 10 may be mounted anywhere else on theparachutist 30 such as, but not limited to, the jumping harness 20 orleg 332 of the parachutist 30 or on the jumping harness 20. Anattachment mechanism (such as, but not limited to, a hooks-and-loopstrap or pocket), allows adjustable positioning of the navigationalcomputer 10 to the jumping harness 20 or any part of the jumpersjumpsuit that is comfortable and out of the way of critical handles ofthe parachute system.

The navigational computer 10 has a display, as discussed more fullybelow, with all necessary information to maneuver and reach the target3. The display receives a signal from the navigational computer 10. Thejumper does not need to change any controls while in flight in order tooperate the navigational computer 10. Other configurations of thenavigational computer 10 are possible. For example, a head mounteddisplay 40 is preferably used for display purposes. Thus, a differentmounting system could be used with such a display. An exemplary heads updisplay, also termed a head mounted display (HMD), that may be used withthe present invention is a display based on the SO-35 Land Warrior headmounted display developed by Rockwell Collins and KaiserElectrode-Optics.

The navigational computer 10 receives positional information 50, such asGPS information, from an orbiting satellite or other similar device 60.The navigational computer 10 is programmed to perform advancedauto-pilot guidance, automatically scaling maps and satellite imagery,way point tracking, team member tracking, alternative targetdesignations, cone of acceptability based on the wind data, as well isthe ability to transition to advanced ground-based functions afterlanding.

Additional features that may be performed by the navigational computer10 include dynamically created, wireless, self-healing, ad-hoc meshnetworks for the automatic creation of peer-to-peer linking of multipleteam members. The peer-to-peer linking allows implementation of keyfeatures to the GUI (graphical user interface) such as allowing teammembers to see each other's location throughout flight and afterlanding. The peer-to-peer linking also enables a single base stationcomputer (such as a laptop) to simultaneously perform and upload Missionplanning on multiple systems and to provide real-time tracking of thetelemetry of each team member.

The peer-to-peer network typically has a range of approximately 60 milesbetween units using 1 watt, spread spectrum 900 mHz transceivers. Thenetwork will be dynamically created, wireless and self-healing. Thenetwork will provide very quick network discovery and synchronization,time domain multiplexing to avoid network collisions, package basedcommunication with 32 bit CRC checks some and allow up to 240 uniquetransmitters and an infinite number of receivers. Other protocols may beused.

The navigational computer 10, FIG. 2, includes a number of functionalelements including a processor or central processing unit 52. Thecentral processing unit (CPU) 52 includes necessary components such asrandom access memory, EEPROM, and optional compact Flash card. Ofcourse, other components could be included in the computer. The computerincludes appropriate software to perform the functions set forth below.

The central processing unit 52 of the navigational computer 10 receivesas input, information from various elements including, but not limitedto, a GPS receiver 60, a compass 54 and/or inertial measurement unit(IMU) 56 (comprising generally of three accelerometers, three rategyros, and three magnetometers) and one or more sensors 58 such as apressure sensor. An RF transceiver 62 is also provided for thepeer-to-peer networking. A display 40 is also provided. In addition, thecentral processing unit 52 may provide an alert 64 such as a flashinglight or audible alarm based on flight conditions such as being offtarget or venturing to close to a team member during descent.

According to an embodiment of the invention, the navigational computer10 includes an RF transceiver 62 for communications between other unitsin the air or on the ground. Multiple navigational computers 10, eachwith an RF transceiver 62, are linked in a peer-to-peer network. In thismanner, information can be shared between computers. For example, thelocation of other jumpers in the team can be automatically transmittedover the network to the navigational computer. Distances and locationsof jumpers can be included as blips on the compass section of thedisplay. Thus, the team may control flight paths for coordinatedoperation. Furthermore, communications mechanisms, such as text orvoice, can be used over the network to allow coordinated efforts.

With the RF transceiver 62 and network 68, the navigational computer 10may also be used for coordination of team operations on the ground.Thus, the navigational computer of the present invention has ongoingutility in the mission after completion of the flight. The preferredembodiment includes a 900 mhz or 1.3 ghz, 1 watt spread spectrum rftransceiver running a masterless TDMA peer-to-peer protocol, althoughother protocols and frequency/powers may be used. Once on the ground,the system's wireless peer-to-peer network enables the units totransition to a useful ground function. The systems will function as anadvanced ground based GPS system enabling team members to visualize eachother's position on the display and communicate. The use of truepeer-to-peer vs. various master slave-networking protocols ensures thenetwork isn't vulnerable to failing upon losing any of the units.

FIG. 3 illustrates one embodiment of the components of the navigationalcomputer 10 in accordance with the present invention. The navigationalcomputer 10 includes a head mounted or other display 40 which canoperate at the temperatures and altitudes for HA/HO jumps. It alsoincludes a number of circuit boards 121, 122, 123, 124 with thenecessary processing hardware to perform the navigational operationsdescribed herein.

According to one embodiment of the invention, the navigational computer10 includes a computer having a central processing unit (CPU), randomaccess memory, EEPROM, and optional compact Flash card. Of course, othercomponents could be included in the computer, or components could beplaced on different circuit boards. The computer includes appropriatesoftware to perform the functions set forth below. Furthermore, thenavigational computer 10 includes a GPS receiver, a compass or optionalinertial measurement unit, and a pressure sensor.

The navigational computer 10 is powered by a DC battery pack 66 whichcan provide hours of capacity at the operating temperatures andaltitudes of the system. The system components are selected to operateat temperatures ranging from approximately −50° C. to approximately +85°C., and at altitudes up to approximately 35,000 feet. Thus, thenavigational computer will operate in the extreme conditions of HA/HOjumps.

According to an embodiment of the invention, the entire unit isapproximate 4.25 inches tall, 6 inches wide, and 2 inches deep. Ofcourse, any other dimensions could be used. In the preferred embodiment,the entire unit is small enough to allow it to be head mounted. Thenavigational computer 10 also includes inputs and outputs forprogramming, providing data, or retrieving data relative to the mission.

FIG. 4 illustrates an embodiment of a display 110 of the navigationalcomputer 10. The display 110, FIG. 4A, preferably includes a firstwindow 109 displaying a map 111 or the like (preferably a satellitemap). The use of a satellite map 111 provides the user with much moreinformation regarding his/her exact position 113 as well as the terrain.Additionally, the satellite map 111 greatly enhances the user's abilityto make decisions in the event a different landing spot or flight pathis needed once the jump has begun by providing the user with valuableinformation of the terrain. The satellite map 111 may also show theposition of other team members 115.

According to the preferred embodiment of the present invention, thedisplay 110 is self-centering such that the user does not need toorientate the display 110 and the display 110 is always pointed in thecorrect direction relative to the user's flight path or even orientationof the user's head. The self-centering feature greatly reduces thelikelihood of the parachutist becoming disorientated during the descent.

The display 110 preferably includes a second window 107 showing at leasta partial navigational “roadmap”, flight path, or look-ahead path 310.The navigational “roadmap” 310 utilizes look ahead navigationalcapabilities to indicate to the jumper his or her travel path 310 giventhe current direction of travel and also providing a “path” 310 on whichthe jumper may “steer” to navigate to the proper target location 330.This feature allows the user to see his/her exact, current location 320as well as see and anticipate any turns in advance, greatly reducinguser fatigue and stress during a descent. Rather than simply providingimmediate instructions (e.g., turn 30 degrees now), the look-aheadflight path 310 allows the user 320 to see not only where he/she is, butalso where he/she is going. The feature looks similar to a driving-typevideo game where a player must steer right or left to keep their car inthe center of the road, with a slight amount of the road visible in thedistance. As parafoils basically have a set glider ratio (which can bevaried not greatly), the autopilot graphical highway need not be trulythree-dimensional but rather two-dimensional, providing look ahead foronly right and left required inputs.

Because the user 320 can see and anticipate the flight path 310, theuser 320 need only control the parachute to line up the arrows or followthe “highway” 310. Consequently, the overall accuracy of the landing isincreased and stress of the user reduced. This feature is alsoparticularly useful when used with a satellite map 111 as discussedabove. Although shown in two different windows 107, 109, the roadmap 310may be overlaid on the satellite map 111. It should be noted, however,that the look-ahead feature may also be used with a standardcompass-based system as shown in FIG. 4B.

As this product is intended for use by many different militarydivisions, the software will allow minor customization of the GUI of thedisplay 110 to best meet the needs of different users. For example,mission planning can set the exact features and look of the GUI from amenu of various options. In addition to the self scaling map, moreskillful operators will likely choose to have additional informationdisplayed in a third window 105, such as, but not limited to, altitude,waypoint tracking and autopilot highway, glider ratio, ETA, heading andbearing to target, and team member locations. A lower skill jumper mayopt to have the minimum required information displayed so as to reducethe likelihood of confusion.

The display 110 includes all of the necessary information for propercompletion of the jump at one time. According to one embodiment, aself-scaling and orienting map is displayed along with the altitude, asuperimposed trace of ones flight path, and an autopilot highway.

Referring specifically to FIG. 4B, the display 110 may also includestatus information on the flight, such as current altitude 122 andovershoot/undershoot 134, i.e., a determination of the landing locationrelative to the target location (how many feet long or short you wouldland if flying straight line to target at current glide ratio). Otherinformation may also be provided in various areas 135 of the display,such as glide ratio, estimated time to landing, heading and bearing totarget.

The navigational computer 10 is programmed to determine the informationto be displayed. In this regard, the target location is programmed intothe computer. The GPS system is used to determine the current locationof the jumper. The GPS system and/or the pressure sensor may also beused to determine the altitude of the jumper (algorithms are included tocalibrate the barometric sensor off the GPS when the accuracy is highenough, when the dilution of precision of the GPS drops due to too fewsatellites in view the system switched to barometric altitude).Additionally, the navigational computer 10 includes a compass/inertialnavigation sensor, which can be used to backup the GPS system or toprovide information in the event of loss of or spoofing of the GPSsignal. Based upon the position and altitude over time, as determined bythe GPS system, pressure sensor, and/or the inertial navigation sensor,the computer calculates the current heading, bearing to target, glideratio, velocity (in various directions), speed over ground, course overground, estimated time to target, and target overshoot or undershoot.This information is feed in to the guidance algorithms to continuouslycalculate an auto pilot flight path to be displayed by the GUI and isdisplayed to the jumper for appropriate flight control. The system canoptionally be provided with motors (not shown) to control the flight ofthe parachutist automatically. This embodiment may be used, for example,as a backup in the event that the parachutist is unable to control theparachute (e.g., due to injury or unconsciousness).

The system may also be used for data logging. A compact Flash memory maybe used to store the calculated information for future review of themission. Additionally other sensors may be included and datalogged.Constructed units have an 8 channel 16 bit a/d converter, whereinchannel 1 is being used by the barometric pressure sensor, leaving 7channels open for connection to other desired sensors, i.e. chemicalweapons sensors and the like. Third-party sensors can be integrated withthe navigational computer. Discrete messages could be communicated toand from the navigational computer and these messages can then betransmitted to either the entire network or to individual units in thenetwork. The protocol for this communication may be customized, fieldupgraded, and encrypted.

According to one embodiment of the invention, calculations are performedusing double precision arithmetic. Distance and azimuth are calculatedusing inverse. The default coordinate system is WGS-84. Of course, otherprocesses, datums, and spheroids may be used. As mentioned above, thepresent invention is not intended to be limited to a device or methodwhich must satisfy one or more of any stated or implied objects orfeatures of the invention and should not be limited to the preferred,exemplary, or primary embodiment(s) described herein. Modifications andsubstitutions by one of ordinary skill in the art are considered to bewithin the scope of the present invention, which is not to be limitedexcept by the following claims.

1-9. (canceled)
 10. A navigational computer for a flexible lifting wingaircraft, comprising: a head mounted display device; a plurality ofnavigational devices, each of said plurality of navigational devicesproviding a navigational signal; a central processing unit, responsiveto said plurality of navigational signals, for processing said pluralityof navigational signals and for providing navigational displayinformation to said display device, said navigational displayinformation including at least look ahead flight path information givingthe user a flight path to navigate to a desired destination; and awireless network link, for establishing communications with at least oneother navigational computer, for providing said navigational informationto said at least one other navigational computer, and for receiving anddisplaying navigational information received from said at least oneother navigational computer.
 11. The navigational computer as claimed inclaim 10 further including guidance algorithms to determine an autopilotflight path and a graphical user interface displaying said direction tosaid user.
 12. The navigational computer as claimed in claim 11 whereinsaid graphical user interface includes at least a two-dimensionalsimulated, look-ahead flight path.
 13. The navigational computer asclaimed in claim 12 wherein said simulated, look-ahead flight pathincludes a three-dimensional simulated, look-ahead flight path.